Anti-vortex tube retaining ring and bore basket

ABSTRACT

An anti-vortex tube (AVT) retaining ring and bore basket is provided and includes a unitary body having an inboard portion, an outboard portion and an intermediate portion. The inboard portion includes a first ring-shaped body with an outer diameter. The outboard portion is configured to support an array of AVTs and includes a second ring-shaped body with an inner diameter larger than the outer diameter of the first ring-shaped body. The intermediate portion includes a flange extending between the outer and inner diameters of the first and second ring-shaped bodies, respectively.

BACKGROUND

Exemplary embodiments of the present disclosure relate generally to gasturbine engines and, in one embodiment, to a hybridized anti-vortex tube(AVT) retaining ring and bore basket.

In a gas turbine engine, air is compressed in a compressor andcompressor air is then mixed with fuel and combusted in a combustor toproduce a high-temperature and high-pressure working fluid. This workingfluid is directed into a turbine in which the working fluid is expandedto generate power. The generated power drives the rotation of a rotorwithin the turbine through aerodynamic interactions between the workingfluid and turbine blades or airfoils. The rotor can be used to driverotations of a propeller or to produce electricity in a generator.

Within certain stages of the compressor, anti-vortex tubes (AVTs) areused to control airflows in front or forward compressor sections and inrear or aft compressor sections. In each case, the tubes are orientedradially and arranged in circumferential arrays and are typically heldin place by complicated parts with multiple components. Assembling thesecomplicated parts and installing them in compressors is time consumingand costly and the complicated parts themselves can be prone to wearbetween mating surfaces and can potentially produce foreign objectdebris (FOD).

Accordingly, a need exists for an AVT retaining ring and bore basketwith a reduced number of components, assembly time and cost that willnot present a risk of production of FOD.

BRIEF DESCRIPTION

According to an aspect of the disclosure, an anti-vortex tube (AVT)retaining ring and bore basket is provided and includes a unitary bodyhaving an inboard portion, an outboard portion and an intermediateportion. The inboard portion includes a first ring-shaped body with anouter diameter. The outboard portion is configured to support an arrayof AVTs and includes a second ring-shaped body with an inner diameterlarger than the outer diameter of the first ring-shaped body. Theintermediate portion includes a flange extending between the outer andinner diameters of the first and second ring-shaped bodies,respectively.

In accordance with additional or alternative embodiments, the unitarybody is additively manufactured.

In accordance with additional or alternative embodiments, the array ofAVTs is arranged circumferentially and each AVT of the array of AVTs isoriented radially.

In accordance with additional or alternative embodiments, the unitarybody is configured for installation within one of front and rear blocksof a gas turbine engine compressor.

In accordance with additional or alternative embodiments, the inboardportion is configured for engagement with an inner diameter of the oneof the front and rear blocks of the gas turbine engine compressor andthe outboard portion is configured for engagement with a boss of the oneof the front and rear blocks of the gas turbine engine compressor.

In accordance with additional or alternative embodiments, the secondring-shaped body defines an array of through-holes through which theAVTs extend and includes a protrusion to support the AVTs.

In accordance with additional or alternative embodiments, the firstring-shaped body defines an airflow pathway, an outlet thereof and aninlet thereof.

According to an aspect of the disclosure, an anti-vortex tube (AVT)retaining ring and bore basket for a front block of a gas turbinecompressor is provided and includes a unitary body having an inboardportion, an outboard portion and an intermediate portion. The inboardportion is engageable with an inner diameter of the front block andincludes a first ring-shaped body with an outer diameter. The outboardportion is engageable with a boss of the front block and to support anarray of AVTs and includes a second ring-shaped body with an innerdiameter larger than the outer diameter of the first ring-shaped body.The intermediate portion includes a flange extending between the outerand inner diameters of the first and second ring-shaped bodies,respectively.

In accordance with additional or alternative embodiments, the unitarybody is additively manufactured.

In accordance with additional or alternative embodiments, the array ofAVTs is arranged circumferentially and each AVT of the array of AVTs isoriented radially.

In accordance with additional or alternative embodiments, the firstring-shaped body is disposable inside inboard ends of bores of rotors offorward-most stages of the front block.

In accordance with additional or alternative embodiments, the secondring-shaped body and the flange are disposed between lower webs ofrotors of aft stages of the front block.

In accordance with additional or alternative embodiments, the secondring-shaped body defines an array of through-holes through which theAVTs extend and includes a protrusion to support the AVTs and the firstring-shaped body defines an airflow pathway, which is fluidlycommunicative with an opening in the front block, an outlet thereof andan inlet thereof which is aft of the outlet.

In accordance with additional or alternative embodiments, the airflowpathway extends inside inboard ends of bores of rotors of at leastforward-most stages of the front block.

According to an aspect of the disclosure, an anti-vortex tube (AVT)retaining ring and bore basket for a rear block of a gas turbinecompressor is provided and includes a unitary body having an inboardportion, an outboard portion and an intermediate portion. The inboardportion is engageable with an inner diameter of the rear block andincludes a first ring-shaped body with an outer diameter. The outboardportion is engageable with a boss of the rear block and to support anarray of AVTs and includes a second ring-shaped body with an innerdiameter larger than the outer diameter of the first ring-shaped body.The intermediate portion includes a flange extending between the outerand inner diameters of the first and second ring-shaped bodies,respectively.

In accordance with additional or alternative embodiments, the unitarybody is additively manufactured.

In accordance with additional or alternative embodiments, the array ofAVTs is arranged circumferentially and each AVT of the array of AVTs isoriented radially.

In accordance with additional or alternative embodiments, the firstring-shaped body is disposable inside inboard ends of bores of rotors ofaft-most stages of the rear block.

In accordance with additional or alternative embodiments, the secondring-shaped body and the flange are disposed between lower webs ofrotors of forward stages of the rear block.

In accordance with additional or alternative embodiments, the secondring-shaped body defines an array of through-holes through which theAVTs extend and includes a protrusion to support the AVTs.

These and other advantages and features will become more apparent fromthe following description taken in conjunction with the drawings.

BRIEF DESCRIPTION OF THE DRAWINGS

The following descriptions should not be considered limiting in any way.With reference to the accompanying drawings, like elements are numberedalike:

FIG. 1 is a partial cross-sectional view of a gas turbine engine;

FIG. 2 is a side view of a section of compressor stages of the gasturbine engine of FIG. 1 in accordance with embodiments;

FIG. 3 is a side view of an AVT retaining ring and bore basket for afront block in accordance with embodiments;

FIG. 4 is a partial perspective view of the AVT retaining ring and borebasket of FIG. 3;

FIG. 5 is a side view of an AVT retaining ring and bore basket for arear block in accordance with embodiments; and

FIG. 6 is a partial perspective view of the AVT retaining ring and borebasket of FIG. 5.

These and other advantages and features will become more apparent fromthe following description taken in conjunction with the drawings.

DETAILED DESCRIPTION

A detailed description of one or more embodiments of the disclosedapparatus and method are presented herein by way of exemplification andnot limitation with reference to the Figures.

FIG. 1 schematically illustrates a gas turbine engine 20. The gasturbine engine 20 is disclosed herein as a two-spool turbofan thatgenerally incorporates a fan section 22, a compressor section 24, acombustor section 26 and a turbine section 28. Alternative engines mightinclude other systems or features. The fan section 22 drives air along abypass flow path B in a bypass duct, while the compressor section 24drives air along a core flow path C for compression and communicationinto the combustor section 26 and then expansion through the turbinesection 28. Although depicted as a two-spool turbofan gas turbine enginein the disclosed non-limiting embodiment, it should be understood thatthe concepts described herein are not limited to use with two-spoolturbofans and may be applied to other types of turbine engines includingthree-spool architectures.

The exemplary gas turbine engine 20 generally includes a low speed spool30 and a high speed spool 32 mounted for rotation about an enginecentral longitudinal axis A relative to an engine static structure 36via several bearing systems 38. It should be understood that variousbearing systems 38 at various locations may alternatively oradditionally be provided, and the location of bearing systems 38 may bevaried as appropriate to the application.

The low speed spool 30 generally includes an inner shaft 40 thatinterconnects a fan 42, a low pressure compressor 44 and a low pressureturbine 46. The inner shaft 40 is connected to the fan 42 through aspeed change mechanism, which in exemplary gas turbine engine 20 isillustrated as a geared architecture 48 to drive the fan 42 at a lowerspeed than the low speed spool 30. The high speed spool 32 includes anouter shaft 50 that interconnects a high pressure compressor 52 and highpressure turbine 54. A combustor 56 is arranged in the gas turbineengine 20 between the high pressure compressor 52 and the high pressureturbine 54. The engine static structure 36 is arranged generally betweenthe high pressure turbine 54 and the low pressure turbine 46. The enginestatic structure 36 further supports the bearing systems 38 in theturbine section 28. The inner shaft 40 and the outer shaft 50 areconcentric and rotate via bearing systems 38 about the engine centrallongitudinal axis A which is collinear with their longitudinal axes.

The core airflow is compressed by the low pressure compressor 44 andthen the high pressure compressor 52, is mixed and burned with fuel inthe combustor 56 and is then expanded over the high pressure turbine 54and the low pressure turbine 46. The high and low pressure turbines 54and 46 rotationally drive the low speed spool 30 and the high speedspool 32, respectively, in response to the expansion. It will beappreciated that each of the positions of the fan section 22, compressorsection 24, combustor section 26, turbine section 28, and fan drive gearsystem 48 may be varied. For example, geared architecture 48 may belocated aft of the combustor section 26 or even aft of the turbinesection 28, and the fan section 22 may be positioned forward or aft ofthe location of geared architecture 48.

The gas turbine engine 20 in one example is a high-bypass gearedaircraft engine. In a further example, the gas turbine engine 20 bypassratio is greater than about six (6), with an example embodiment beinggreater than about ten (10), the geared architecture 48 is an epicyclicgear train, such as a planetary gear system or other gear system, with agear reduction ratio of greater than about 2.3 and the low pressureturbine 46 has a pressure ratio that is greater than about five. In onedisclosed embodiment, the gas turbine engine 20 bypass ratio is greaterthan about ten (10:1), the fan diameter is significantly larger thanthat of the low pressure compressor 44, and the low pressure turbine 46has a pressure ratio that is greater than about five 5:1. Low pressureturbine 46 pressure ratio is pressure measured prior to inlet of lowpressure turbine 46 as related to the pressure at the outlet of the lowpressure turbine 46 prior to an exhaust nozzle. The geared architecture48 may be an epicycle gear train, such as a planetary gear system orother gear system, with a gear reduction ratio of greater than about2.3:1. It should be understood, however, that the above parameters areonly exemplary of one embodiment of a geared architecture engine andthat the present disclosure is applicable to other gas turbine enginesincluding direct drive turbofans.

A significant amount of thrust is provided by the bypass flow B due tothe high bypass ratio. The fan section 22 of the gas turbine engine 20is designed for a particular flight condition—typically cruise at about0.8 Mach and about 35,000 feet (10,688 meters). The flight condition of0.8 Mach and 35,000 ft (10,688 meters), with the engine at its best fuelconsumption—also known as “bucket cruise Thrust Specific FuelConsumption (‘TSFC’)”—is the industry standard parameter of 1 bm of fuelbeing burned divided by 1 bf of thrust the engine produces at thatminimum point. “Low fan pressure ratio” is the pressure ratio across thefan blade alone, without a Fan Exit Guide Vane (“FEGV”) system.

As will be described below, an AVT retaining ring and bore basket isprovided and has a reduced number of components and a reduced risk ofproducing FOD as compared to conventional assemblies.

With continued reference to FIG. 1 and with additional reference to FIG.2, AVT retaining ring and bore baskets 201 and 202 are provided forinstallation in the front and rear blocks 203 and 204, respectively, ofthe compressor section 24 of the gas turbine engine 20. Each of the AVTretaining ring and bore baskets 201 and 202 includes a unitary body 210,which has an inboard portion 220, an outboard portion 230 and anintermediate portion 240. The unitary body 210 can be additivelymanufactured into a single continuous feature or welded together into asingle continuous feature. The inboard portion 220 includes a firstring-shaped body 221 with an outer diameter OD. The outboard portion 230is configured to support an array of AVTs 231 and includes a secondring-shaped body 232 with an inner diameter ID. The inner diameter ID islarger than the outer diameter OD of the first ring-shaped body 221. Thearray of AVTs 231 is arranged circumferentially and each AVT 231 isoriented to extend along the radial dimension of the gas turbine engine20. The intermediate portion 240 includes a flange 241 that extendsbetween the outer diameter OD of the first ring-shaped portion 221 andthe inner diameter ID of the second ring-shaped body 232.

In accordance with embodiments, while FIG. 2 illustrates that the AVTretaining ring and bore basket 201 is provided for installation in thefront block 203 and that the AVT retaining ring and bore basket 202 isprovided for installation in the rear block 204, this is not required.For example, the AVT retaining ring and bore basket 201 can be providedfor installation in the front block 203 with or without installation ofthe AVT retaining ring and bore basket 202 in the rear block 204 and theAVT retaining ring and bore basket 202 can be provided for installationin the rear block 204 with or without installation of the AVT retainingring and bore basket 201 in the front block 203.

In the case of the AVT retaining ring and bore basket 201 being providedfor installation in the front block 203, the inboard portion 220 isconfigured for engagement with an inner diameter of the front block 203of the compressor section 24 of the gas turbine engine 20 and theoutboard portion 230 is configured for engagement with a boss 205 of thefront block 203 of the compressor section 24 of the gas turbine engine20. In the case of the AVT retaining ring and bore basket 202 beingprovided for installation in the rear block 204, the inboard portion 220is configured for engagement with an inner diameter of the rear block204 of the compressor section 24 of the gas turbine engine 20 and theoutboard portion 230 is configured for engagement with a boss 205 of therear block 204 of the compressor section 24 of the gas turbine engine20.

In the case of the AVT retaining ring and bore basket 201 being providedfor installation in the front block 203, the second ring-shaped body 232defines an array of through-holes 233 through which the AVTs 231 extendand includes a protrusion 234 to support the AVTs 231 and the firstring-shaped body 221 defines an airflow pathway 222, an outlet 223thereof and an inlet 224 thereof. During operational conditions,airflows proceed through the front block 203 via inlet 2031 and aftbetween lower webs of the rotors of the forward-most stages of the frontblock 203 and the first ring-shaped body 221. In doing so, the airflowsoccupy space between the lower webs. Eventually, the airflows proceedinto the airflow pathway 222 via the inlet 224 and leave the airflowpathway 222 via the outlet 223 before proceeding through the front block203 via outlet 2032. Additional airflows flow inwardly through the AVTs231.

In the case of the AVT retaining ring and bore basket 202 being providedfor installation in the rear block 204, the second ring-shaped body 232defines the array of through-holes 233 through which the AVTs 231 extendand includes the protrusion 234 to support the AVTs 231. Duringoperational conditions, airflows proceed inwardly through the AVTs 231and aft between lower webs of the rotors of the aft-most stages of therear block 204 and the first ring-shaped body 221. In doing so, theairflows occupy space between the lower webs. Eventually, the airflowsproceed through the rear block 204 via outlet 2041.

With reference to FIGS. 3 and 4, an AVT retaining ring and bore basket301 is provided for a front block 02 of the compressor section 24 of thegas turbine engine 20 of FIGS. 1 and 2. The AVT retaining ring and borebasket 301 is similar to the AVT retaining ring and bore basket 201 andlike elements need not be described in further detail but to note thatthe AVT retaining ring and bore basket 301 includes a unitary body 310,which can be additively manufactured or welded and which has an inboardportion 320 that includes a first ring-shaped body 321, an outboardportion 330 that is engageable with a boss of the front block andincludes a second ring-shaped body 332 and an intermediate portion 340that includes a flange 341 extending between the first ring-shapedportion 321 and the second ring-shaped body 332. The first ring-shapedbody 321 is disposable inside inboard ends of bores of rotors offorward-most stages of the front block and the second ring-shaped body332 and the flange 341 are disposed between lower webs of aft stages ofthe front block. The second ring-shaped body 332 defines an array ofthrough-holes 333 through which the AVTs extend and includes aprotrusion 334 to support the AVTs. The first ring-shaped body 321defines an airflow pathway 322, an outlet 323 thereof and an inlet 324thereof which is aft of the outlet 323.

With reference to FIGS. 5 and 6, an AVT retaining ring and bore basket501 is provided for a rear block of the compressor section 24 of the gasturbine engine 20 of FIGS. 1 and 2. The AVT retaining ring and borebasket 501 is similar to the AVT retaining ring and bore basket 202 andlike elements need not be described in further detail but to note thatthe AVT retaining ring and bore basket 501 includes a unitary body 510,which can be additively manufactured or welded and which has an inboardportion 520 that includes a first ring-shaped body 521, an outboardportion 530 that is engageable with a boss of the rear block andincludes a second ring-shaped body 532 and an intermediate portion 540that includes a flange 541 extending between the first ring-shapedportion 521 and the second ring-shaped body 532. The first ring-shapedbody 521 is disposable inside inboard ends of bores of rotors ofaft-most stages of the rear block and the second ring-shaped body 532and the flange 541 are disposed between lower webs of forward stages ofthe rear block. The second ring-shaped body 532 defines an array ofthrough-holes 533 through which the AVTs extend and includes aprotrusion 534 to support the AVTs.

Benefits of the features described herein are the provision of an AVTretaining ring and bore basket that has a reduced number of componentsand a reduced risk of producing FOD as compared to conventionalassemblies.

The term “about” is intended to include the degree of error associatedwith measurement of the particular quantity based upon the equipmentavailable at the time of filing the application.

The terminology used herein is for the purpose of describing particularembodiments only and is not intended to be limiting of the presentdisclosure. As used herein, the singular forms “a”, “an” and “the” areintended to include the plural forms as well, unless the context clearlyindicates otherwise. It will be further understood that the terms“comprises” and/or “comprising,” when used in this specification,specify the presence of stated features, integers, steps, operations,elements, and/or components, but do not preclude the presence oraddition of one or more other features, integers, steps, operations,element components, and/or groups thereof.

While the present disclosure has been described with reference to anexemplary embodiment or embodiments, it will be understood by thoseskilled in the art that various changes may be made and equivalents maybe substituted for elements thereof without departing from the scope ofthe present disclosure. In addition, many modifications may be made toadapt a particular situation or material to the teachings of the presentdisclosure without departing from the essential scope thereof.Therefore, it is intended that the present disclosure not be limited tothe particular embodiment disclosed as the best mode contemplated forcarrying out this present disclosure, but that the present disclosurewill include all embodiments falling within the scope of the claims.

What is claimed is:
 1. An anti-vortex tube (AVT) retaining ring and borebasket, comprising: a unitary body having an inboard portion, anoutboard portion and an intermediate portion, the inboard portioncomprising a first ring-shaped body with an outer diameter, the outboardportion being configured to support an array of AVTs and comprising asecond ring-shaped body with an inner diameter larger than the outerdiameter of the first ring-shaped body, wherein an axial end of theoutboard portion opposite the intermediate portion is axially alignedwith a point on the inboard portion, and the intermediate portioncomprising a flange extending between the outer and inner diameters ofthe first and second ring-shaped bodies, respectively, wherein thesecond ring-shaped body defines an array of through-holes through whichthe AVTs extend and comprises a protrusion to support the AVTs.
 2. TheAVT retaining ring and bore basket according to claim 1, wherein theunitary body is additively manufactured.
 3. The AVT retaining ring andbore basket according to claim 1, wherein the array of AVTs is arrangedcircumferentially and each AVT of the array of AVTs is orientedradially.
 4. The AVT retaining ring and bore basket according to claim1, wherein the unitary body is configured for installation within a rearblock of a gas turbine engine compressor.
 5. The AVT retaining ring andbore basket according to claim 4, wherein the outboard portion isconfigured for engagement with a boss of a rear block of the gas turbineengine compressor.
 6. The AVT retaining ring and bore basket accordingto claim 1, wherein the first ring-shaped body defines an airflowpathway, an outlet thereof and an inlet thereof.
 7. An anti-vortex tube(AVT) retaining ring and bore basket for a front block of a gas turbinecompressor and comprising: a unitary body having an inboard portion, anoutboard portion and an intermediate portion, the inboard portionengageable with an inner diameter of the front block and comprising afirst ring-shaped body with an outer diameter, the outboard portionengageable with a boss of the front block and configured to support anarray of AVTs and comprising a second ring-shaped body with an innerdiameter larger than the outer diameter of the first ring-shaped body,and the intermediate portion comprising a flange extending between theouter and inner diameters of the first and second ring-shaped bodies,respectively, wherein the second ring-shaped body defines an array ofthrough-holes through which the AVTs extend and comprises a protrusionto support the AVTs.
 8. The AVT retaining ring and bore basket accordingto claim 7, wherein the unitary body is additively manufactured.
 9. TheAVT retaining ring and bore basket according to claim 7, wherein thearray of AVTs is arranged circumferentially and each AVT of the array ofAVTs is oriented radially.
 10. The AVT retaining ring and bore basketaccording to claim 7, wherein the first ring-shaped body is disposableinside inboard ends of bores of rotors of forward-most stages of thefront block.
 11. The AVT retaining ring and bore basket according toclaim 7, wherein the second ring-shaped body and the flange are disposedbetween lower webs of rotors of aft stages of the front block.
 12. TheAVT retaining ring and bore basket according to claim 7, wherein thefirst ring-shaped body defines an airflow pathway, which is fluidlycommunicative with an opening in the front block, an outlet thereof andan inlet thereof which is aft of the outlet.
 13. The AVT retaining ringand bore basket according to claim 12, wherein the airflow pathwayextends inside inboard ends of bores of rotors of at least forward-moststages of the front block.
 14. An anti-vortex tube (AVT) retaining ringand bore basket for a rear block of a gas turbine compressor andcomprising: a unitary body having an inboard portion, an outboardportion and an intermediate portion, the inboard portion engageable withan inner diameter of the rear block and comprising a first ring-shapedbody with an outer diameter, the outboard portion engageable with a bossof the rear block and configured to support an array of AVTs andcomprising a second ring-shaped body with an inner diameter larger thanthe outer diameter of the first ring-shaped body, and the intermediateportion comprising a flange extending between the outer and innerdiameters of the first and second ring-shaped bodies, respectively. 15.The AVT retaining ring and bore basket according to claim 14, whereinthe unitary body is additively manufactured.
 16. The AVT retaining ringand bore basket according to claim 14, wherein the array of AVTs isarranged circumferentially and each AVT of the array of AVTs is orientedradially.
 17. The AVT retaining ring and bore basket according to claim14, wherein the first ring-shaped body is disposable inside inboard endsof bores of rotors of aft-most stages of the rear block.
 18. The AVTretaining ring and bore basket according to claim 14, wherein the secondring-shaped body and the flange are disposed between lower webs ofrotors of forward stages of the rear block.
 19. The AVT retaining ringand bore basket according to claim 14, wherein the second ring-shapedbody defines an array of through-holes through which the AVTs extend andcomprises a protrusion to support the AVTs.